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This specification describes the general connectors, contacts, and backshells in their shape and characteristic for cabin systems for commercial aircrafts. ARINC 600, ARINC 404, and ARINC 801 connector specifications are published as independent standards.

The purpose of this document is to provide an overview of data networking standards recommended for use in commercial aircraft installations. These standards provide a means to adapt commercially defined networking standards to an aircraft environment. It refers to devices such as bridges, switches, routers and hubs and their use in an aircraft environment. This equipment, when installed in a network topology, can optimize data transfer and overall avionics performance.

The purpose of this document is to establish guidelines that should be observed during initial design, production, and maintenance of aircraft components, and to present short-term and long-term strategies to minimize the costs and impacts associated with decreasing availability of components.

The difficulty in locating crash sites has prompted international efforts for alternatives to quickly recover flight data. This document describes the technical requirements and architectural options for the Timely Recovery of Flight Data (TRFD) in commercial aircraft. ICAO and individual Civil Aviation Authorities (CAAs) levy these requirements. The ICAO Standards and Recommended Practices (SARPs) and CAA regulations cover both aircraft-level and on-ground systems. This report also documents additional system-level requirements derived from the evaluation of ICAO, CAA, and relevant industry documents and potential TRFD system architectures. It describes two TRFD architectures in the context of a common architectural framework and identifies requirements. This report also discusses implementation recommendations from an airplane-level perspective.

The growing need for an efficient worldwide airspace system management, generated by an increasing traffic load, requires new capabilities for air-ground data communication technologies. In order to cope with these requirements, the Federal Aviation Administration (FAA), EUROCONTROL, and the International Civil Aviation Organization (ICAO) have jointly made specific recommendations for candidate technologies for the airport surface communication network. In the SESAR project, the Aeronautical Mobile Airport Communication System (AeroMACS) technology is being developed in such a way to provide next generation broadband and wireless data communications for airport surface applications (i.e. Air Traffic Control ? ATC, Airline Operational Communications ? AOC, and surface vehicles services).

Abstract A key problem of the construction of fully electric aircraft is the limited energy density of battery packs. It is generally accepted that this can only be overcome via new, denser battery chemistry together with a further increase in the efficiency of power utilization. One appealing approach for achieving the latter is using laser-assisted filler-based joining technologies, which offers unprecedented flexibility for achieving battery cell connections with the least possible electrical loss. This contribution presents our results on the effect of various experimental and process parameters on the electrical and mechanical properties of the laser-formed bond.

Abstract Improving the energy performance of batteries can increase the reliability of electric aircraft. To achieve this goal, battery management systems (BMS) are required to keep the temperature within the battery pack and cells below the safety limits and make the temperature distribution as even as possible. Batteries have a limited service life as a result of unwanted chemical reactions, physical changes that cause the loss of active materials in the structure, and internal resistance increase during the charging and discharging cycle of the battery. These changes usually affect the electrical performance of batteries. Battery life can be increased only by reducing or preventing unwanted chemical reactions. Lithium-ion (Li-ion) batteries are a suitable option due to their high specific energy and energy density advantages. In this study, the necessity of heat management is emphasized. The discharge tests of the Li-ion battery provided 94.6 Wh under 10C and 90.9 Wh under 1C.

Abstract The range of an aircraft is determined by the amount of energy that its batteries can store. Today, larger batteries are used to increase the range of electric vehicles, although energy efficiency decreases as the weight of the vehicles increases. Among the elements, lithium (Li) is the lightest and has the highest electrochemical potential. Therefore, the use of Li-ion batteries is recommended for hybrid aircraft. In addition, Li-ion batteries are the most common type of battery that is used in portable electronic devices such as smartphones, tablets, and laptops. However, Li-ion batteries may explode due to temperature. Therefore, the thermal analysis of Li-ion batteries was investigated both experimentally and numerically. Li-ion batteries were connected in series (the number is 9). Noboru’s theory of heat generation was discussed in the estimation of energy data.

Abstract The supersession of metallic alloys with lightweight, high-strength composites is popular in the aircraft industry. However, aviation electronic enclosures for large format batteries and high power conversion electronics are still primarily made of aluminum alloys. These aluminum enclosures have attractive properties regrading structural integrity for the heavy internal parts, electromagnetic interference (EMI) suppression, electrical bonding for the internal cells, and/or electronics and failure containment. This paper details a lightweight carbon fiber composite chassis developed at Meggitt Sensing Systems (MSS) Securaplane, with a copper metallic mesh co-cured onto the internal surfaces resulting in a 50% reduction in weight when compared to its aluminum counterpart. In addition to significant weight reduction, it provides equal or improved performance with respect to EMI, structural and flammability performance.

pilots, air traffic controllers, dispatchers, aviation meteorologists

This activity is focused on more electric and all electric type power systems for air vehicles. The scope of which includes source, distribution and user contributions to electrical power quality, failure modes, coordination, system reliabilty and robustness, impacts of being flight critical and the gaps which exist in present standards and guidance documents.

This AIR addresses the use of Software tools to supplement or automate human activities in the development of systems, but not the hardware or software items within those systems. If a systems development tool is also used in the scope of hardware or software item development, for that usage it would then become subject to the guidance presented in DO-254 and DO-178B/C, respectively.

AS 6413 and slash sheets /1 & /2 hold the main information for testing of battery packaging. This document holds further information and expansion of philosophy, clarification etc. surrounding the testing and industry needs.

This AIR will provide a basic understanding of STPA and how it can be applied to development and safety assessment of civil aircraft. It will explain, by way of an example, the information needed to begin STPA, the expected STPA outputs, and the phases of aircraft development and safety assessment that can be supported by STPA.

Clarify the role of the human considerations in Functional Hazard Assessments by identifying the sufficient input information regarding those considerations from the development process, how failure conditions may use that information, and what information the safety assessment process provides to other processes, particularly Human Factors, to assure those aspects of failure conditions are valid.

This AIR would examine the applicability of ARP 4754 and ARP 4761 to UAS and would identify the shortcomings in both recommended practices with regards to the specific technical aspects needed for UAS development.

This SAE Aerospace Information Report is intended to provide advanced methods for wire selecting and sizing in aerospace application as a continuation of AIR6540, Fundamentals in Wire Selection and Sizing for Aerospace Applications. Also, it will provide valuable information for the electrical design engineer to verify the proper wire selection and validate a set of system design requirements which includes meeting environmental and installation constraints.

EPS stability is an essential property that defines EPS ability to provide secure operation under required range of operation scenario. Power system stability is defined as “the ability of an electric power system, for a given initial operating condition, to regain a state of operating equilibrium after being subjected to a physical disturbance, with most system variables bounded so that practically the entire system remains intact”. This is applicable for AC and DC systems and has to address steady state conditions, transient conditions as well as high power loads connection / disconnection on the network.

This standard is intended to demonstrate and document the control of the potential hazards from lithium cells or batteries (UN 3090 and 3480) when transported as cargo on aircraft. [still need to identify if we are addressing global (external fire) or local (battery internal failures)] This standard addresses the need to control the hazards which might arise from a failure from an individual cell by containing the hazards within the package. This specific hazards addressed within this standard are: • Uncontrolled fire • Rapid overpressure pulse within compartment

This category specification provides a minimum performance standard that may be used for mitigation means, in addition to the foundation specification (AS6413), to provide external fire thermal threat capability which supports the safe shipment of lithium batteries as cargo on aircraft. This slash sheet provides information and testing to assist or augment the performance of the packaging used for shipping of lithium batteries. If protective equipment and measures are used, the performance of the battery package under the challenge of external heat and fire may be improved and enhanced.